A liquid fueled gas generator is described which was designed to simulate the effluent produced by a solid propellant hydrocarbon fuel, typical of those used for ducted rocket propulsion, by burning a very fuel-rich mixture of liquid hydrocarbons with gaseous oxygen. The gas generator was built to function as a tool for the development of components of the ramburner portion of the ducted rocket system and to provide a means for studying the thermochemical processes involved in the production of the fuel-rich effluent and its secondary combustion with air in the ramburner. Successful operation has been documented at total fuel and oxidizer flow rates through the gas generator of 0.20 kg/sec (0.44 lbs/sec) during direct-connect ducted rocket combustion tests.
The development of a liquid fueled gas generator for ducted rocket research
Entwicklung eines Flüssigkraftstoff-Gasgenerators für Untersuchungen über Raketenantriebe mit Leitungskanälen
Joint Army-Navy-NASA-Air Force (JANNAF) Propulsion Meeting, 1990 ; 1 , Sep ; 313-320
1991
8 Seiten, 5 Bilder, 1 Tabelle, 7 Quellen
Aufsatz (Konferenz)
Englisch
THE DEVELOPMENT OF A LIQUID FUELED GAS GENERATOR FOR DUCTED ROCKET RESEARCH
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